【作者】 赵东林；

【导师】 张立同； 成来飞；

【作者基本信息】 西北工业大学 ， 材料学， 2006， 硕士

【摘要】 碳/碳化硅陶瓷基复合材料(C/SiC)是一种新型防热结构一体化材料,具有优异的耐高温性能、抗氧化性能、摩擦性能以及低密度等特点,是第二代空天飞行器防热结构一体化的关键材料。根据跨大气层飞行器再入大气的气动加热环境和C/SiC复合材料构件的应用特点,要求C/SiC陶瓷基复合材料具有优异的应力氧化烧蚀性能,以满足防热结构一体化构件重复使的要求;优异的高温连接性能,以满足制造大型复杂防热结构一体化构件的需要;优异的高温高载低速摩擦磨损性能,以满足方向舵、襟翼等活动防热结构一体化构件的使用要求。因此,研究C/SiC陶瓷基复合材料的高温应力氧化烧蚀、高温连接以及高温高载低速摩擦磨损环境性能,对其在空天飞行器上的应用具有重要意义。 本文根据材料再入环境的应力氧化烧蚀、高温连接以及高温高载低速摩擦磨损性能模拟的要求,研制了用于材料环境性能研究的再入大气环境实验模拟设备。该模拟设备由常压亚音速燃气流风洞、材料力学试验机与伺服传动装置等部分组成。主要研究内容与结果如下: 1.设计并制造常压亚音速燃气流风洞,实现了再入大气热物理化学环境的模拟。该风洞加热效率高,几分钟内就可加热到最高温度1800℃;燃气成分与大气成分相近,可长时间(约30min)持续运行。 2.设计并制造伺服传动装置,实现了方向舵、襟翼等活动控制构件铰链的机械转动模拟。该装置能够对高温高载条件下的试验件进行转速控制(0～128r/min)和转矩控制(0～50N·m)。 3.设计并制造应力氧化烧蚀、高温连接以及高温高载低速摩擦磨损性能实验模拟的试验件和夹具,试验件和夹具在实验过程中未发生非正常破坏,表明试验件与夹具的设计合理可行。 4.进行了C/SiC材料的应力氧化烧蚀、高温连接和高载低速摩擦磨损性能的实验模拟验证,结果表明材料再入大气环境性能实验模拟设备达到了设计要求。更多还原

【Abstract】 C/SiC ceramic matrix composite is a new kind of thermo-structure material. It has been a key thermo-structure material for the 2nd generation spacecraft because of excellent high temperature performance, oxidation resistance, friction property and low density, etc. According to aerodynamic heating environment of re-entry atmosphere and specialties of C/SiC components, C/SiC ceramic matrix composite has excellent stressed oxidation and ablation resistance for the reuse of thermo-structure components. Its good hot joint property meets the need of manufacture for big complex thermo-structure components. It has good friction and wear property at high temperature, high load and low rotation speed, which satisfies the application of movable thermo-structure components such as rudder, body flap, etc. So it is important to research the stressed oxidation and ablation resistance property, hot joint property and friction and wear property of C/SiC ceramic matrix composite for applications in spacecraftAccording to research materials’ stressed oxidation and ablation property, hot joint property and friction and wear property at high temperature, high load and low rotation speed in re-entry atmosphere environment, an experimental-anologic facility was designed and manufactured. It was composed of common pressure subsonic gas-fired wind tunnel, material test machine and servo-drive instrument. The main contents and results are as follows:1. A common pressure subsonic gas-fired wind tunnel was designed and manufactured. It is feasible to simulate the re-entry hot physical chemistry environment. The heating efficiency of this wind tunnel is high, it can reach 1800℃ in a few minutes. The elements of fired gas are close to atmosphere. The wind tunnel has a long run-time (nearly 30min).2. Servo-drive instrument was designed and manufactured. It is feasible to simulate the movement of the hinge of movable components such as body flap, rudder, etc. It can control the rotation speed (0~128r/min) and torque (0-50N · m ) of test samples at high temperature and high load.3. Samples and clamps were designed and made to research stressed oxidation and ablation property, hot joint property and friction and wear property at high temperature, high load and low rotation speed. The samples and clamps were not damaged abnormally during testing. So the design of samples and clamps are viable.4. C/SiC stressed oxidation and ablation test, hot joint test and friction and wear test were successfully conducted by the experimental-anologic facility. The results of tests show that the facility meets the design specification.更多还原